Quick disconnect coupling systems and related methods

ABSTRACT

Quick disconnect devices for high pressure fluid transfer, and associated systems and methods are disclosed. A representative quick disconnect system includes a first connector and a second connector. The second connector can have an opening sized and shaped to receive a first end of the first connector. The second connector can include a poppet positioned to open the first connector when the first connector is connected to the second connector. The second connector can include an inner sleeve moveable between a first position wherein the poppet head forms a fluid-tight seal with the annular seat of the inner sleeve, and a second position wherein the second end portion is open to permit fluid flow through the end portion of the inner sleeve. In some embodiments, the inner sleeve is pressure balanced in every direction.

TECHNICAL FIELD

The present disclosure is directed generally to quick disconnectcouplings, and associated systems and methods.

BACKGROUND

Rockets have been used for many years to launch human and non-humanpayloads into orbit. Such rockets delivered the first humans to spaceand to the moon, and have launched countless satellites into the Earth'sorbit and beyond. Such rockets are used to propel unmanned space probesand more recently to deliver structures, supplies, and personnel to theorbiting international space station.

In order to reach orbit, rockets and other launch vehicles must beprovided with fuel, hydraulic fluid, coolant, and/or other fluids, manyof which are transferred and stored at very high pressures. Onechallenge associated with transferring high-pressure fluid to therockets is avoiding fluid leaks at the connections between the rocketsand fluid sources (e.g., tanks). Aspects of the present disclosure aredirected to addressing this and other challenges.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a partially schematic, side elevation view of a representativerocket, a fluid source, and a quick disconnect system connecting therocket to the fluid source.

FIG. 2 is a cross-sectional side view of a first connector of a quickdisconnect system configured in accordance with embodiments of thepresent technology.

FIG. 3 is a cross-sectional side view of a second connector of a quickdisconnect system configured in accordance with embodiments of thepresent technology.

FIG. 4A is an end view of the first connector of FIG. 2 mated with thesecond connector of FIG. 3.

FIG. 4B is a cross-sectional side view of the first and secondconnectors of FIG. 4A, taken along cut-plane A-A of FIG. 4A when apoppet of the second connector first contacts a piston of the firstconnector.

FIG. 4C is the cross-sectional side view of the first and secondconnectors shown in FIG. 4B, at a point when an abutment sleeve of thesecond connector first contacts an outer housing of the first connector.

FIG. 4D is a close-up cross-sectional side view of the first connectorof FIG. 2, taken along the cut-plane B-B of FIG. 4A.

FIG. 4E is the cross-sectional side view of the first and secondconnectors shown in FIG. 4B, when an inner sleeve of the secondconnector first abuts the abutment sleeve.

FIG. 4F is the cross-sectional side view of the first and secondconnectors shown in FIG. 4B, when the first connector is fully coupledwith the second connector.

FIG. 5A is an end view of another first connector of a quick disconnectsystem configured in accordance with embodiments of the presenttechnology.

FIG. 5B is a cross-sectional side view of the first connector of FIG.5A, taken along cut-plane C-C of FIG. 5A.

FIG. 5C is a cross-sectional side view of the first connector of FIG.5A, taken along cut-plane D-D of FIG. 5A.

FIG. 6 is a cross-sectional side view of another second connector of aquick disconnect system configured in accordance with embodiments of thepresent technology.

FIG. 7A is a cross-sectional side view of the first connector of FIGS.5A-5C and the second connector of FIG. 6 at a point when a poppet of thesecond connector first contacts a piston of the first connector.

FIG. 7B is a cross-sectional side view of the first and secondconnectors shown in FIG. 7A, at a point when an outer flange of an innersleeve of the second connector first contacts an outer housing of thefirst connector.

FIG. 7C is a cross-sectional side view of the first and secondconnectors shown in FIG. 7A, at a point when the first connector isfully coupled with the second connector.

DETAILED DESCRIPTION

Embodiments of the technology disclosed herein are directed generally toquick disconnect systems for providing fluid connections between two ormore fluid vessels. For example, the quick disconnect systems disclosedherein can be used to fluidly connect fluid systems on and/or in alaunch vehicle to an external fluid source. The quick disconnect systemsdisclosed herein can include both ground-side and flight-side connectorsconfigured to couple and decouple with each other. One or both of theground-side and flight-side connectors can include components configuredto reduce or eliminate leaks, pressure blow-off, and/or other adverseevents when the connectors are coupled to, and decoupled from, eachother. For example, one or both of the connectors can include pressurebalanced structures configured to operate with little or no forceimbalance imparted from pressurized fluid within the connectors when theconnectors are coupled to each other. As used herein, “pressurebalanced” refers to components for which, when the connectors arecoupled to each other, pressure forces imparted to the components by thepressurized fluid within the connectors are balanced in the axial,radial, and circumferential directions, with respect to the longitudinalaxes of the connectors. In other words, the pressure “footprints” of thepressure balanced components in are equal when observed in opposingaxial directions, in opposing radial directions, and in opposingcircumferential directions. In some embodiments, the flight and/orground-side connectors can include one or more features that areisolated from the pressurized fluid within the connectors. Such isolatedfeatures can be configured to operate without being subject to pressureforces from the pressurized fluid.

To avoid obscuring other aspects of the disclosure, several detailsdescribing structures and processes that are well-known and oftenassociated with such quick disconnect systems are not set forth in thefollowing description. Moreover, although the following disclosure setsforth several embodiments, several other embodiments can have differentconfigurations, arrangements, and/or components than those described inthis section. In particular, other embodiments may have additionalelements, and/or may lack one or more of the elements described belowwith reference to FIGS. 1-7C.

FIG. 1 is a partially schematic illustration of a representative system10 configured in accordance with embodiments of the present technology.The system 10 can include a vehicle 20 (e.g., a launch vehicle) having asingle or a multi-stage configuration. In the representative embodimentshown in FIG. 1, the vehicle 20 includes one or more internal fluidsystems 30 and/or one or more external fluid systems 40. The fluidsystems 30, 40 can be, for example, fuel tanks, hydraulic systems,coolant systems, and/or other systems requiring fluid. The fluid used bythe fluid systems can include, without limitation, gaseous hydrogen,gaseous helium, gaseous nitrogen, gaseous oxygen, hydrogen peroxide,and/or other suitable fluids. In some embodiments, the fluid systems areconfigured for cryogenic uses and may require liquid fluids.

The various fluid systems 30, 40 can be filled or refilled using anexternal fluid source 50. The external fluid source 50 can be, forexample, a tank, truck, or other fluid container. Often, the fluidwithin the fluid source 50 is stored at a very high pressure. Forexample, the fluid can be maintained at pressures up to or exceeding6,500 pounds per square inch gauge (PSIG). In some embodiments, thefluid within the fluid source 50 is stored at pressures between 0 PSIGand 7,500 PSIG. The fluids may be maintained at temperatures between−60° F. and 400° F. In some embodiments, the fluids are maintained atcryogenic temperatures.

The external fluid source can be connected to one or more of the fluidsystems 30, 40 via a quick disconnect system 60. The quick disconnectsystem can include a first (e.g., flight-side) connector 100 and asecond (e.g., ground-side) connector 200 configured to connect to, anddisconnect from, each other. The flight-side connector 100 can bepermanently or temporarily connected to the fluid systems 30, 40 andconfigured to prevent ingress or egress of fluid through the flight-sideconnector 100 when disconnected from the ground-side connector 200. Theground-side connector 200 can be removably or permanently connected tothe external fluid source 50 and configured to prevent ingress or egressof fluid through the ground-side connector 200 when disconnected fromthe flight-side connector 100.

FIG. 2 is a cross-sectional illustration of an embodiment of theflight-side connector 100 shown in FIG. 1, disconnected from theground-side connector 200 (FIG. 1). The flight-side connector 100 caninclude a longitudinal axis 102, an outer sleeve 104 having a first end106 (e.g., a ground-side end), and a second end 108 (e.g., a flight-sideend) opposite the first end along the longitudinal axis 102. The firstend 106 can include an opening or inlet. The second end 108 can includean outlet. In some embodiments, the second end 108 includes a matingstructure configured to connect the flight-side connector 100 to alaunch vehicle 20 (FIG. 1) or other fluid destination. The matingstructure can be, for example, a flange 112 having one or more bores 114through which fasteners may be inserted. The first end 106 of the outersleeve 104 can include a sleeve mating face 116 configured to engagewith a portion of the ground-side connector 200, described further withreference to FIG. 2.

The flight-side connector 100 can include an inner housing 120positioned at least partially within the outer sleeve 104. In someembodiments, the inner housing 120 is positioned entirely within theouter sleeve 104. The inner housing 120 can have a first end 122 (e.g.,a leading end or ground-side end) and a second end 124 (e.g., aflight-side end) opposite the first end 122 of the inner housing 120.The inner housing 120 can include a piston chamber 130 having an openingat the first end 122 of the inner housing 120. In some embodiments, theinner housing 120 includes one or more apertures 132 that form fluidpaths or passages through a portion of the inner housing 120.

As is also shown in FIG. 2, the flight-side connector 100 can include apiston 140 (e.g., a flight-side piston). The piston 140 can bepositioned at least partially within one or both of the outer sleeve 104and the piston chamber 130 of the inner housing 120. The piston 140 canhave a mating face 142 at the end of the piston 140 nearest the firstend 106 of the outer sleeve 104. In some embodiments, the mating face142 of the piston 140 is flush with the first end 106 (e.g., with themating face 116) of the outer sleeve 104 when the piston is in a firstposition (e.g., a closed position). An end of the piston 140 oppositethe mating face can be positioned within the piston chamber 130. Thepiston 140 can include an inner bore 144 (e.g., a piston bore) extendingthrough all or most of the piston 140 in a direction parallel to thelongitudinal axis 102 of the flight-side connector 100.

A piston retainer 150 may be positioned at least partially within thepiston chamber 130. The piston retainer 150 can have, for example, anelongate shape. In some embodiments, the piston retainer 150 extends atleast partially through the piston bore 144. The piston retainer 150 canbe fixed at one end to the inner housing 120. The opposite end of thepiston retainer 150 can include retainer mating face 152 and an outerflange 154 configured to engage with an inner flange 156 of the pistonbore 144. The outer flange 154 of the piston retainer 150 can limit themovement of the piston 140 in the ground direction and can form a sealwith the inner flange 156 of the piston bore 144 when the flight-sideconnector 100 is in a closed or sealed configuration (as illustrated inFIG. 2). In some embodiments, the piston retainer 150 can include a vent160 through at least a portion of the piston retainer 150 which can ventthe piston chamber 130 to an exterior of the flight-side connector 100.For example, the vent 160 of the piston retainer 150 can be in fluidcommunication with an outer sleeve vent 162 (e.g., through a channel(not shown) in the inner housing 120). The outer sleeve vent 162 can, inturn, be in fluid communication with the ambient environment surroundingthe quick disconnect system 60.

In some embodiments, the piston chamber 130 includes a spring 164 orother biasing structure configured to bias the piston 140 in the grounddirection. The piston 140 can include a spring retaining portion 166 onthe side of the piston opposite the mating face 142. The springretaining portion 166 can be, for example, an annular groove or pocketconfigured to receive one end of the spring 164. The other end of thespring 164 can abut a wall of the piston chamber 130.

The flight-side connector 100 can include a fluid flow path extendingbetween the first end 106 of the outer sleeve and the second end 108 ofthe outer sleeve. As illustrated in FIG. 2, a first portion 170 of thefluid path can extend in an annular fashion from the first end 106 ofthe outer sleeve 104 between the inner housing 120 and an inner wall ofthe outer sleeve 104. The fluid path can continue through the one ormore apertures 132 in the inner housing 120 to the second end 108 of theouter sleeve 104. The outer sleeve 104 can include a seal 172 (e.g., apiston seal) adjacent the first end 106 of the outer sleeve 104. Thepiston seal 172 can be, for example, an elastomeric O-ring or othersimilar structure configured to seal an outer wall of the piston 140against the outer sleeve 104 when the piston 140 is in the closedposition. The flight-side connector 100 can include a chamber seal 174near the first end 122 of the inner housing 120. The chamber seal 174can also be an elastomeric O-ring or similar structure configured toprevent fluid passage between the piston 140 and the inner housing 104when the piston 140 is in the closed position.

FIG. 3 is a cross-sectional illustration of an embodiment of theground-side connector 200 shown in FIG. 1, disconnected from theflight-side connector 100 (FIG. 2). The ground-side connector 200 canhave a longitudinal axis 202 and can include a quick disconnect portion204 and an attachment portion 206 connected to the quick disconnectportion 204. The quick disconnect portion 204 can be configured toconnect to, and disconnect from, the ground-side end of the flight-sideconnector 100. The attachment portion 206 can be configured to connectto a tank or other external fluid source 50.

The quick disconnect portion 204 of the ground-side connector 200 caninclude an outer sleeve 210 having a first end 212 (e.g., a ground-sideend) and a second end 214 (e.g., a flight-side end). The second end 214of the outer sleeve 210 of the ground-side portion 200 can include anopening 216 configured to receive the ground-side end of the flight-sideconnector 100. In some embodiments, the second end 214 of the outersleeve 210 is chamfered, tapered, or otherwise formed to guide theground-side end of the flight-side connector 100 into the second end 214of the outer sleeve 210.

The ground-side connector 200 can include a poppet sleeve 220 positionedat least partially within the outer sleeve 210 of the ground-sideconnector 200. In some embodiments, the poppet sleeve 220 has agenerally cylindrical shape. The poppet sleeve 220 can have a closed end222 at or near the first end 212 of the outer sleeve 210 and an open end224 opposite the closed end 222 along the longitudinal axis 202. Theclosed end 222 of the poppet sleeve 220 can be affixed to the outersleeve 210 of the ground-side connector 200 via an adhesive, weldment,fastener, or other suitable attachment structure or method. In theillustrated embodiment, the closed end 222 of the poppet sleeve 220includes an outer flange 226 that is wedged and/or compressed betweenthe attachment portion 206 (e.g., a pivot adapter 230 thereof) and aninner step 232 of the outer sleeve 210.

The ground-side connector 200 can include a poppet 234 positioned atleast partially within the poppet sleeve 220. The poppet 234 can includea head portion 236 having a mating face 240. The mating face 240 of thepoppet 234 can be sized and shaped to match the size and shape of themating face 142 of the piston 140 of the flight-side connector 100 (FIG.2). In some embodiments, the mating face 240 of the poppet 234 has anouter perimeter that matches an outer perimeter of the mating face 142of the piston 140. The poppet 234 can include a poppet stem 242extending from the head portion 236 in a direction opposite the matingface 240 of the poppet 234. In some embodiments, the poppet 234 is fixedto the poppet sleeve 220 such that the poppet 234 is prevented frommoving with respect to the poppet sleeve 220. In some embodiments, thepoppet stem 242 can be affixed or otherwise connected to the closed end222 of the poppet sleeve 220.

The ground-side connector 200 can include an inner sleeve 250surrounding at least a portion of the poppet 234. In some embodiments,the inner sleeve 250 is positioned at least partially within the poppetsleeve 220. The inner sleeve 250 can have a generally cylindrical shape.A sleeve seal 252 (e.g., an O-ring or other sealing structure) can bepositioned between the inner sleeve 250 and the poppet sleeve 220 andcan prevent fluid from passing past the inner sleeve 250 between theinner sleeve 250 and the poppet sleeve 220. The sleeve seal 252 can bepositioned, for example, in an annular groove on an outer wall of theinner sleeve 250.

The inner sleeve 250 can have a first end 254 (e.g., a ground-side end)and a second end 256 (e.g., a flight-side end) opposite the first end254. The first end 254 of the inner sleeve 250 can abut a spring 258 orother biasing structure positioned between the first end 254 of theinner sleeve 250 and the closed end 222 of the poppet sleeve 220. Thespring 258 can bias the inner sleeve 250 into contact with the poppet234 (e.g., the head portion 236 of the poppet 234). In particular, thesecond end 256 of the inner sleeve 250 can include a poppet seat 260against which the poppet 234 (e.g., the head portion 236 of the poppet234) can rest. The poppet seat 260 can be, for example, an inner taperedportion of the second end 256 of the inner sleeve 250. The ground-sideconnector 200 can include a poppet seal 262 configured to seal theinterface between the head portion 236 of the poppet 234 and the poppetseat 260. The poppet seal 262 can be, for example, an O-ring or othersimilar sealing structure. The poppet seal 262, as illustrated, can bepositioned in an annular groove on the head portion 236 of the poppet234.

In some embodiments, the ground-side connector 200 includes an abutmentsleeve 270. The abutment sleeve 270 can be positioned at least partiallywithin the outer sleeve of the ground-side connector 200. The abutmentsleeve 270 can surround at least a portion of the inner sleeve 250, thepoppet 234, and the poppet sleeve 220. The abutment sleeve 270 caninclude a mating surface 272 (e.g., a first end) nearest the second end214 of the outer sleeve 210. The mating surface 272 of the abutmentsleeve 270 can be configured to engage with a portion of the flight-sideconnector 100, as described in more detail below. An opposite end (e.g.,a second end) of the abutment sleeve 270 can include an outer flange 274or other structure configured to engage with the outer sleeve 210 (e.g.,an inner flange 276 thereof) and to prevent movement of the abutmentsleeve 270 past a predetermined position toward the second end 214 ofthe outer sleeve 210. A spring 278 or other biasing structure cansurround at least a portion of the poppet sleeve 220 and can bias theabutment sleeve 270 toward the second end 214 of the outer sleeve 210.The spring 278 can be seated between the outer flange 274 of theabutment sleeve 270 and an outer projection 284 of the poppet sleeve220. The abutment sleeve 270 can include an inner flange 280 at or nearthe mating surface 272 of the abutment sleeve 270. The inner flange 280of the abutment sleeve 270 can be configured to contact an outer flange282 or ridge of the inner sleeve 250 when the abutment sleeve 270 movestoward the first end 214 of the outer sleeve 210 of the ground-sideconnector 200. In some embodiments, the outer flange 282 is an annularprotrusion from a radially-outer surface of the inner sleeve 250. Insome embodiments, the outer flange 282 includes a plurality ofprotrusions separated by gaps in the circumferential direction withrespect to the longitudinal axis 202 of the ground-side connector 200.

As illustrated in FIG. 3, the attachment portion 206 can include a pivotadapter 230, introduced above. The first end 286 of the pivot adapter230 can form an inlet to the ground-side connector 200. The pivotadapter 230 can include one or more ridges, ribs, flanges, or otherstructures extending radially outwardly from the pivot adapter 230. Forexample, the pivot adapter 230 can include an annular ridge 288 having agimbaled (e.g., rounded) surface 289 on a radially-outward portionthereof.

The attachment portion 204 can include a retaining ring 290 configuredto engage with the gimbaled surface of the annular ridge 288 of thepivot adapter 230. The retaining ring 290 can have an inner gimbaledportion 292 shaped and sized to permit the pivot adapter 230 to tiltwith respect to the retaining ring 290. The retaining ring 290 and theannular ridge 288 of the pivot adapter 230 can be captured between awall 294 of the external fluid source 50 (FIG. 1) and a retainer 296.The retainer 296 can be affixed to the wall 294 via fasteners,weldments, adhesives, and/or other suitable attachment methods andstructures. In some embodiments, the retainer ring 290 can have an outerdiameter smaller than an inner diameter of the space 298 in which theannular ring is captured. The retainer ring 290 can also be thinner thanthe space 298 in a direction parallel to the longitudinal axis 202 ofthe ground-side connector 200 to allow the pivot adapter 230 to movewith respect to the wall 294 of the external fluid source 50 in adirection parallel to the longitudinal axis 202. In total, the interfacebetween the annular ridge 288 and the retaining ring 290 can permit thepivot adapter 230 and/or the external fluid source 50 to move relativeto each other with six degrees of freedom. More specifically, the pivotadapter 230 can rotate (e.g., about the longitudinal axis 202 of theground-side connector 200), translate, and tilt with respect to the wall294 of the external fluid source 50. With reference to FIG. 1, thisfreedom of motion can reduce the risk of damage to the quick disconnectsystem 60, to the launch vehicle 20, and/or to the external fluid source50 as the flight-side connector 100 and the ground-side connector 200are connected to, and disconnected from, each other.

Returning to FIG. 3, the ground-side connector 200 can include a fluidpath extending from the first end 286 of pivot adapter 230 through tothe second end 214. The first end 286 of the pivot adapter 230 can forman inlet to the fluid path. The fluid path can continue through aninterior bore 297 of the pivot adapter 230, and through one or moreapertures 299 formed in the closed end 222 of the poppet sleeve 220. Thefluid path continues through the interior of the poppet sleeve 220 andthrough an interior of the inner sleeve 250. When the inner sleeve 250is engaged with the poppet 234, the fluid path ends at the poppet seal262. When, however, the inner sleeve 250 is withdrawn from the headportion 236 of the poppet 234, the fluid path continues around the headportion 236 of the poppet 234 and through the second end 214 of theouter sleeve 210 of the ground-side connector 200.

FIG. 4A is an end view of the flight-side connector 100 and theground-side connector 200 in an engaged or coupled configuration. Asillustrated, the inner housing 120 can include two or more apertures132. In some embodiments, the inner housing 120 includes three, four, ormore apertures 132. In some embodiments, all of the apertures 132 havethe same cross-sectional area as measured perpendicular to thelongitudinal axis 102 of the flight-side connector 100 or, asillustrated in FIG. 4A, one or more of the apertures 132 can have across-sectional area greater than or smaller than the cross-sectionalarea of another aperture 132.

FIGS. 4B-4E are cross-sectional illustrations of the flight-sideconnector 100 and the ground-side connector 200 in various stages ofcoupling. Specifically, FIG. 4B illustrates the connectors 100, 200 ininitial contact with each other, FIGS. 4C and 4D illustrate partialcoupling wherein the abutment sleeve 270 of the ground-side connector200 initially contacts the mating surface 116 of the outer sleeve 104 ofthe flight-side connector 100, FIG. 4E illustrates the point at whichthe inner sleeve 250 contacts the abutment sleeve 270, and FIG. 4Fillustrates the flight-side connector 100 fully coupled with theground-side connector 200. The cross-sections of FIGS. 4B, 4C, 4E, and4F are taken along the cut-plane A-A of FIG. 4A. The cross-section ofFIG. 4D is taken along the cut-plane B-B of FIG. 4A. As illustrated inFIG. 4F, fluid from a fluid source flows through the fluid paths of boththe flight-side connector 100 and the ground-side connector 200 when theflight-side connector 100 is fully coupled with the ground-sideconnector 200, as illustrated by the broken lines. The connectors 100,200 can be configured to operate independent of the rotational alignmentbetween the connectors 100, 200 about the respective longitudinal axes102, 202.

Referring now to FIG. 4B, during an initial stage of coupling theflight-side connector 100 to the ground-side connector 200, the firstend 106 of the outer sleeve 104 of the flight-side connector 100 isinserted into the second end 214 of the outer sleeve 210 of theground-side connector 200. Both the tapered opening 216 of the outersleeve 210 of the ground-side connector 200 and the above-described sixdegrees-of-freedom of motion allowed by the annular ridge 288 andretaining ring 290 of the ground-side connector 200 can reduce theprecision required to mate or couple the flight-side connector 100 tothe ground-side connector 200.

As the outer sleeve 104 of flight-side connector 100 is further insertedinto the outer sleeve 210 of the ground-side connector 200, the matingface 240 of the poppet 234 contacts the mating face 142 of the piston140. As discussed above, the mating face 240 of the poppet 234 can besized and shaped to match the size and shape of the mating face 142 ofthe piston 140 such that the mating face 240 covers all or substantiallyall of the mating face 142 of the piston 140.

Moving to FIG. 4C, further advancement of the outer sleeve 104 offlight-side connector 100 is further inserted into the outer sleeve 210of the ground-side connector 200, bringing the abutment sleeve 270 intocontact with the outer sleeve 104. Specifically, the mating surface 272of the abutment sleeve 270 contacts the mating surface 116 of the outersleeve 104. At this point in the coupling process, the head portion 236is still in contact with the inner sleeve 250, keeping the ground-side200 closed. Also, the piston seal 172 can be in contact with the headportion 236 such that the flight-side connector 100 remains closed withrespect to the ground-side connector 200.

The head portion 236 of the poppet 234 begins pushing the piston 140further into the piston chamber 130 against the bias force of the spring164 before or as the abutment sleeve 270 contacts the outer sleeve 104.Displaced air or other fluid in the piston chamber 130 can be ventedthrough the vent 160 in the piston retainer 150. The inner flange 156 ofthe piston bore 144 moves away from the outer flange 154 of the pistonretainer 150 to break the seal between the inner flange 156 and theouter flange 154. Breaking this seal vents the piston bore 144 into thepiston chamber 130.

The vented fluid/air from the piston chamber 130 can further passthrough a vent passage 161 (also shown in FIG. 4D) in the inner housing120. The vent passage 161 can fluidly connect to an annular orsemi-annular circumferential passage 163 on an outer surface of theinner housing 120. The passage 163 can extend between the vent passage161 and outer sleeve vent 162 to provide a continuous fluid pathway fromthe piston chamber 130 to the environment surrounding the quickdisconnect system 60, via the outer sleeve vent 162 shown in FIG. 4C. Insome embodiments, all or a portion of the passage 163 is formed in aradially inner wall of the outer sleeve 104.

Referring to FIG. 4E, as the outer sleeve 104 of flight-side connector100 is further inserted into the outer sleeve 210 of the ground-sideconnector 200, the outer flange 282 of the inner sleeve 250 makescontact with the inner flange 280 of the abutment sleeve 270. Contactbetween the outer flange 282 and the inner flange 280 can preventfurther movement of the inner sleeve 250 in the flight direction (e.g.,toward the piston 140) with respect to the poppet head 236 and/or outerhousing 140 of the flight-side connector 100.

The inner sleeve 250 can remain in contact with the poppet head 236and/or with the poppet seal 262 at this point in the coupling process.Continued contact between the inner sleeve 250 (e.g., the second end 256thereof) and the poppet head 236 and/or poppet seal 262 maintains theground-side connector 200 in closed configuration.

Before or after the outer flange 282 of the inner sleeve 250 contactsthe inner flange of the abutment sleeve 270, the head portion 236 of thepoppet 234 further pushes the piston 140 into the piston chamber 130.The second end 256 of the inner sleeve 250 can also pass at leastpartially into the outer sleeve 104 of the flight-side connector 100.The piston seal 172 can form a seal against the radially-outer wall ofthe inner sleeve 250 as the inner sleeve 250 enters the outer sleeve104.

As the outer sleeve 104 of flight-side connector 100 is further insertedinto the outer sleeve 210 of the ground-side connector 200, asillustrated in FIG. 4F, the head portion 236 of the poppet 234 entersthe piston chamber 130 and pushes the piston 140 further into the pistonchamber 130. The chamber seal 174 can engage with an outer surface ofthe poppet head portion 236 to prevent fluid flow past the poppet headportion 236 into the piston chamber 130.

As the flight-side connector 100 is moved further into the ground-sideconnector 200, the outer sleeve 104 of the flight-side connector 100pushes the abutment sleeve 270 toward the first end 212 of the outersleeve 210 of the ground-side connector 200, against the biasing forceof the spring 278. The abutment sleeve 270 (e.g., the inner flange 280thereof) pushes the inner sleeve 250 (e.g., the outer flange 282thereof) toward the first end 212 of the outer sleeve 210 of theground-side connector 200 and away from the head portion 236 of thepoppet 234. As the inner sleeve 250 moves away from the head portion 236of the poppet 234, the poppet seal 262 disengages from the inner sleeve250 and the fluid path of the ground-side connector 200 opens to allowfluid to flow through the ground-side connector 200 and the flight-sideconnector 100, as indicated in dashed lines in FIG. 4F.

The components of the flight-side connector 100 and the ground-sideconnector 200 can be dimensioned such that the quick disconnect system60 is fully opened when the mating face 240 of the poppet 234 contactsthe piston retainer 150. In some embodiments, full mating is achievedwhen the outer flange 282 of the inner sleeve 250 of the ground-sideconnector 200 is pushed against the open end 224 of the poppet sleeve220.

When the flight-side connector 100 is disconnected or decoupled from theground-side connector 200, the poppet head portion 236 (e.g., the poppetseal 262) can re-seat with the inner sleeve 250. This re-seating processcan occur before the seal between the outer sleeve 104 (e.g., the pistonseal 172) of the flight-side portion 100 and the inner sleeve 250 isbroken. Accordingly, fluid flow through the quick disconnect system 60can be shut off before the flight-side connector 100 separates from theground-side connector 200, thereby avoiding any fluid leaks duringdisconnection. Additionally, the piston 140 returns to its initialclosed position (FIG. 2) before the poppet head portion 236 separatesfrom the piston 140, and before the seal between the outer sleeve 104 ofthe flight-side portion 100 and the inner sleeve 250 is broken.Reestablishing the seal between the piston 140 and the piston seal 172can reduce or eliminate the risk of fluid leaks into the piston chamber130 during disconnection.

FIGS. 5A-5C illustrate an embodiment of a flight-side connector 100 aconfigured in accordance with the embodiments of the present technology.The flight-side connector 100 a is similar both structurally andfunctionally to the flight-side connector 100 described above.Specifically, components of the flight-side connector 100 a that aresimilar to or the same as components of the flight-side connector 100are identified with like reference numbers having an added “a” (e.g.,piston 140 a of the connector 100 a is generally similar to the piston140 described above). The descriptions of the flight-side connector 100a will therefore be limited to describing those components and featuresthat are notably different from the corresponding components andfeatures of the flight-side connector 100. In some embodiments, theflight-side connector 100 a can be coupled with one or both of theground-side connector 200 or the ground-side connector 200 a describedbelow. FIG. 5B is a cross-sectional view of the flight-side connector100 a taken along the cut-plane C-C of FIG. 5A, and FIG. 5C is across-sectional view taken along the cut-plane D-D of FIG. 5A.

Referring to FIG. 5B, the piston chamber vent 160 a can extend through aportion of the inner housing 120 a rather than through the pistonretainer 150 a. For example, the vent 160 a can extend through a backwall (e.g., a wall nearest the second end 124 a of the inner housing 120a) of the piston chamber 130 a. In some embodiments, the vent 160 aextends parallel to the longitudinal axis 102 a of the flight-sideconnector 100 a.

The vent 160 a can fluidly connect with the vent passage 161 a. The ventpassage 161 a can extend through a portion of the inner housing 120 aand extend to an annular or semi-annular passage 163 a on a radiallyouter surface of the inner housing 120 a. The passage 163 a can be influid communication with the outer sleeve vent 162 a. The respectivevents and passages 160 a, 161 a, 162 a, and 163 a can provide fluidcommunication between the piston chamber 130 a and the ambientenvironment surrounding the flight-side connector 100 a. As illustratedin FIG. 5C, the one or more apertures 132 a of the inner housing 120 acan be similar to or generally the same as the one or apertures 132described above.

FIG. 6 illustrates an embodiment of a ground-side connector 200 aconfigured in accordance with the embodiments of the present technology.The ground-side connector 200 a is similar both structurally andfunctionally to the ground-side connector 200 described above.Specifically, components of the ground-side connector 200 a that aresimilar to or the same as components of the ground-side connector 200are identified with like reference numbers having an added “a” (e.g.,tapered opening 216 a of the connector 200 a is substantially similar tothe tapered opening 216 described above). In some embodiments, theground-side connector 200 a can be coupled with one or both of theflight-side connector 100 a or the flight-side connector 100. Thedescriptions of the ground-side connector 200 a will therefore belimited to describing those components and features that are notablydifferent from the corresponding components and features of theground-side connector 200.

As illustrated in FIG. 6, the ground-side connector 200 a can include anindentation 237 a on the mating face 240 a of the poppet head 236 a. Theindentation 237 a can be sized and shaped to receive a portion of thepiston retainer 150, 150 a (FIG. 7C) during coupling between theground-side connector 200 a and a flight-side connector.

The inner sleeve 250 a can be modified with respect to the inner sleeve250 described above. For example, the inner sleeve 250 a of FIG. 6 caninclude an outer flange 282 a having a spring abutment portion 283 aconfigured to engage with the spring 258 a and an inner abutment portion285 a configured to engage the open end 224 a of the piston sleeve 220a. In the illustrated embodiment of the ground-side connector 200 a, theabutment sleeve 270 is removed. Removing the abutment sleeve can allowfor the use of a single spring (e.g., the spring 258 a) for the innersleeve 250 a without requiring an additional spring for an abutmentsleeve.

The pivot adaptor 230 a can include an annular ring 288 a that is formedseparately from the pivot adaptor 230 a. The annular ring 288 a canfunction in a manner similar to or the same as the annular ridge 288described above. In some embodiments, the annular ring 288 a has anouter gimbaled surface 289 a that engages directly with an innergimbaled surface 292 a of the wall 294 a and/or retainer 296 a.

Moving to FIGS. 7A-7B, as the outer sleeve 104 a of the flight-sideconnector 100 a advances further into the outer sleeve 210 a of theground-side connector 200 a, the poppet 234 a can push the piston 140 afurther into the piston chamber 130 a. Fluid (e.g., air) within theinner bore 144 a and the piston chamber 130 a can be vented through thevent 160 a, the vent passage 161 a, and the outer sleeve vent 162 a asdescribed above with respect to FIG. 5B.

The inner sleeve 250 a can remain in sealed contact with the poppet head236 a at least until the outer flange 282 a of the inner sleeve 250 aabuts the mating surface 116 a of the outer sleeve 104 a. The pistonseal 172 a can remain in sealed contact with at least one of the piston140 a, the poppet head 236 a, and the inner sleeve 150 a when theflight-side connector 100 a is decoupled from the ground-side connector200 a in a manner similar to or the same as that described above withrespect to the poppet seal 172.

Turning now to FIG. 7C, advancing the outer sleeve 104 a of theflight-side connector 100 a further into the outer sleeve 210 a of theground-side connector 200 a can cause the poppet 234 a to push thepiston 140 a further into the piston chamber 130 a until the piston head236 a contacts the piston retainer 150 a, until the piston 140 acontacts a back wall of the piston chamber 130 a, and/or until the innerabutment portion 285 a of the outer flange 282 a contacts the open end224 a of the poppet sleeve 220 a. During this transition, the outersleeve 104 a can push the inner sleeve 250 a away from the poppet head236 a, thereby opening the ground-side connector 200 a and permittingfluid flow through both the ground-side connector 200 a and flight-sideconnector 100 a as illustrated by the broken arrows.

Receipt of a portion of the piston retainer 150 a into the indentation237 a of the poppet head 236 can allow the piston 140 a to have a longerstroke than would be the case if the indentation 237 a were not presenton the mating face 240 a of the poppet head 236 a.

One feature of several of the embodiments described above with referenceto FIGS. 1-7C is that the respective flight and ground-side connectors100, 200 do not impart fluid-induced forces on each other duringconnection and disconnection. This is due, at least in part, to using a“pressure balanced” inner sleeve 250 and by isolating the piston 140from the pressurized fluid. More specifically, the portions of the innersleeve 250 exposed to high-pressure fluid in directions parallel to thelongitudinal axis of the ground-side connector 200 are generally equalin both the flight direction and ground direction (i.e., the footprintsor projected surface areas of the exposed surfaces of the inner sleeve250 are equal in both the flight direction and the ground direction).Additionally, the portions of the inner sleeve 250 exposed tohigh-pressure in directions perpendicular to the longitudinal axis ofthe ground-side connector 200 are evenly circumferentially distributed,causing the net pressure force in directions perpendicular to thelongitudinal axis to be zero or approximately zero. Fluid-induced forcesfrom the flight-side connector 100 to the ground-side connector 200 arealso reduced by using a vented piston 140 that is isolated from thepressurized fluid. More specifically, as described above, the matingface 240 of the poppet 234 fully covers, or at least generally covers,the mating face 142 of the piston during connection and disconnection.Covering the mating face 142 of the piston 140 isolates the piston 140from the high-pressure fluid in the connectors 100, 200, allowing thepiston 140 to operate without receiving forces from the pressurizedfluid within the connectors 100, 200. Further, venting the opposite sideof the piston 140 (e.g., venting the piston chamber 130) reduces oreliminates pressure buildup on the opposite side of the piston 140,thereby reducing or eliminating fluid-induced forces (e.g., forcesgenerated from the pressurized fluid) from the piston 140 to the poppet234 or poppet head portion 236. Avoiding fluid-induced forces on therespective connectors 100, 200 during connection and disconnection canreduce or eliminate the risk of damage to the connectors 100, 200 andthe associated fluid destinations and fluid sources attached thereto.

Another feature of several of the embodiments described above is thatthe connectors 100, 200 connect and disconnect from each other without,or at least generally without, fluid leaks. This, in turn, improves theefficiency of the system.

Still a further feature of embodiments of connectors 100, 200 describedabove is that they can facilitate fluid connection and disconnectionwhile under pressure. More specifically, because the connectors 100, 200can connect and disconnect without leaks, the pressure of fluid withinthe connectors can be maintained at or near operating pressures withlittle or no risk of pressure blow-off.

From the foregoing, it will be appreciated that specific embodiments ofthe present technology have been described herein for purposes ofillustration, but that various modifications may be made withoutdeviating from the technology. For example, the various springs aredescribed herein as providing biasing forces on the various componentsof the quick disconnect system 40. In some embodiments, one or more ofthe springs may be replaced with elastomeric sleeves or other biasingstructures. In still further embodiments, pneumatic or hydraulic forcesmay be used instead of or in addition to the biasing force provided bythe springs. Certain aspects of the technology described in the contextof particular embodiments may be combined or eliminated in otherembodiments. For example, in some embodiments described above, thepoppet sleeve 220 and pivot adapter 230 of the ground-side connector 200are described as being separate parts that may be mated together orotherwise connected during manufacture. In some embodiments, the poppetsleeve 220 and pivot adapter 230 are formed as a single unitary part.Further, while advantages associated with certain embodiments of thedisclosed technology have been described in the context of thoseembodiments, other embodiments may also exhibit such advantages, and notall embodiments need necessarily exhibit such advantages to fall withinthe scope of the present technology. Accordingly, the disclosure andassociated technology can encompass other embodiments not expresslyshown or described herein.

As used herein, the terms “generally” and “approximately” refer tovalues or characteristics within a range of ±10% from the stated valueor characteristic, unless otherwise indicated. As used herein, “and/or”as in “A and/or B” refers to A alone, B alone, and/or both A and B.

I/We claim:
 1. A quick disconnect system for transmitting, comprising: afirst connector comprising: a first outer sleeve having a first end anda second end; and a second connector comprising: a second outer sleevehaving an opening sized and shaped to receive the first end of the firstouter sleeve; a poppet positioned at least partially within the secondouter sleeve and positioned to open the first connector when the firstconnector is connected to the second connector; and an inner sleevepositioned at least partially within the second outer sleeve and having:a first end portion; and a second end portion opposite the first endportion and having an annular seat; wherein: the inner sleeve ismoveable between a first position wherein the poppet head forms afluid-tight seal with the annular seat of the inner sleeve, and a secondposition wherein the second end portion is open to permit fluid flowthrough the second end portion; and the inner sleeve is pressurebalanced in every direction when in the first position, when in thesecond position, and when transitioning between the first position andthe second position.
 2. The system of claim 1, wherein the secondconnector further comprises an abutment sleeve surrounding at least aportion of the inner sleeve, and wherein the abutment sleeve ispositioned to push the inner sleeve away from the first connector as thefirst connector is connected with the second connector.
 3. The system ofclaim 2, wherein the abutment sleeve comprises an inner flange, whereinthe inner sleeve further comprises an outer flange, and wherein theinner flange of the abutment sleeve is positioned to push the outerflange of the inner sleeve as the first connector is connected to thesecond connector.
 4. The system of claim 1, wherein the poppet is fixedwith respect to the second outer housing.
 5. The system of claim 1,wherein the second connector further comprises a poppet sleevepositioned at least partially within the second outer housing, thepoppet sleeve having a closed end and an open end, wherein the poppet isfixed to the closed end of the poppet sleeve.
 6. The system of claim 1,wherein the second connector further comprises a poppet sleevepositioned at least partially within the second outer housing, thepoppet sleeve having a closed end and an open end, wherein the innersleeve is positioned at least partially within the poppet sleeve.
 7. Thesystem of claim 6, wherein the second connector further comprises abiasing element positioned to bias the inner sleeve away from the closedend of the poppet sleeve and toward the head of the poppet.
 8. Thesystem of claim 7, wherein the biasing element is a spring.
 9. A quickdisconnect system for transmitting a fluid: a first connectorcomprising: a first outer sleeve having a first end and a second end;and a piston having a mating face and positioned at least partiallywithin the inner housing, the piston being moveable between a firstposition in which the piston closes the first end of the outer sleeveand a second position in which the first end of the outer sleeve isopen; and a second connector connectable to the second fluid vessel andcomprising a poppet having a head with a mating face sized and shaped tocontact the mating face of the piston; wherein: the mating face of thepoppet is sized and shaped to cover the mating face of the piston whenthe mating face of the poppet contacts the mating face of the piston; aside of the piston opposite the mating face is vented to an ambientenvironment surrounding the first connector; and the piston is isolatedfrom the fluid when in the first position, when in the second position,and during transition between the first position and the secondposition.
 10. The system of claim 9, wherein the first connector furthercomprises an inner housing positioned at least partially within thefirst outer sleeve, the inner housing having a piston chamber vented toan exterior of the quick disconnect system, wherein the piston ispositioned at least partially within the inner housing.
 11. The systemof claim 10, wherein the first connector further comprises a pistonretainer positioned at least partially within the piston chamber andhaving a first end affixed to the inner housing and a second end havingan outer flange, wherein the piston includes an internal bore having aninner flange, and wherein the outer flange is positioned to engage withan inner flange to prevent movement of the piston past the first end ofthe first outer sleeve.
 12. The system of claim 9, wherein the matingface of the piston is flush with the first end of the first outer sleevewhen the piston is in the first position.
 13. The system of claim 9,wherein the mating face of the head of the poppet has an outerperimeter, and wherein the mating face of the piston has an outerperimeter identical to the outer perimeter of the mating face of thehead of the poppet.
 14. The system of claim 9, wherein the secondconnector further comprises a gimbaled surface positioned to mate with acorresponding gimbaled surface of a supporting structure.
 15. The systemof claim 14, wherein the gimballed surface is sized and shaped to permitthe second connector to move with respect to the supporting structurewith six degrees of freedom when the second connector is connected tothe supporting structure.
 16. The system of claim 9, wherein the firstconnector further comprises a biasing element within the piston chamber,wherein the biasing element biases the piston away from the second endof the first outer sleeve.
 17. The system of claim 9, wherein both thefirst connector and the second connector are sized and shaped to connectand disconnect from each other without fluid leaks.
 18. The system ofclaim 9, wherein both the first connector and the second connector areconfigured to accommodate fluids having pressures up to 6,500 PSIG. 19.A method of fluidly connecting a first fluid vessel to a second fluidvessel, the method comprising: engaging a mating face of a piston of afirst connector with a mating face of a poppet of a second connectorsuch that the mating face of the poppet covers the mating face of thepiston; pushing the piston toward the first fluid vessel with thepoppet; and pushing an inner sleeve of the second connector toward thesecond fluid vessel to separate the inner sleeve from the poppet;wherein: the first connector is connected to the first fluid vessel; thesecond connector is connected to the second fluid vessel; separating theinner sleeve from the poppet permits fluid flow from the fluid sourcearound a perimeter of the mating face of the poppet; and the innersleeve is pressure balanced in every direction.
 20. The method of claim19, further comprising venting a side of the piston opposite the matingface of the piston as the poppet pushes the piston toward the fluiddestination.
 21. The method of claim 19, wherein the piston is isolatedfrom fluid from the second fluid vessel as the piston is pushed towardthe first fluid vessel.
 22. The method of claim 19, wherein the firstfluid vessel is a fuel tank of a rocket.
 23. The method of claim 19,wherein the inner sleeve is exposed to equal fluid pressure forces alonga longitudinal axis of the second connector in both directions along alongitudinal axis of the second connector.